 | |
| Country of origin | USSR |
|---|---|
| Date | 1958-1960 |
| Designer | OKB-456, V.Glushko |
| Associated LV | R-14, Kosmos-3 and Kosmos-3M |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | AK-27I / UDMH |
| Mixture ratio | 2.5 |
| Configuration | |
| Chamber | 2 |
| Nozzle ratio | 18.8 |
| Performance | |
| Thrust, vacuum | 887 kN (199,000 lbf) |
| Thrust, sea-level | 740 kN (170,000 lbf) |
| Chamber pressure | 7.355 MPa (1,066.8 psi) |
| Specific impulse, vacuum | 289 s (2.83 km/s) |
| Specific impulse, sea-level | 246 s (2.41 km/s) |
| Dimensions | |
| Length | 2,205 mm (86.8 in) |
| Diameter | 2,260 mm (89 in) |
| Dry mass | 575 kg (1,268 lb) |
| Used in | |
| R-14, Kosmos-3 and Kosmos-3M first stage | |
| References | |
| References | [1][2][3][4][5][6] |
The RD-215 (Russian: Ракетный Двигатель-215, romanized: Raketnyy Dvigatel-215, lit. 'Rocket Engine 215', GRAU index: 8D513) was a dual nozzle liquid-fuel rocket engine, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with AK-27 oxidizer (a mixture of 73% nitric acid and 27% dinitrogen tetroxide [N2O4] with iodine as a passivant). It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU index: 8D514).[2] The RD-215 was developed by OKB-456 for Yangel's Yuzhmash R-14 (8K65) ballistic missile. Its variations were also used on the Kosmos-1, Kosmos-3 and Kosmos-3M launch vehicles.[1]
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